1、Oktober 2005DEUTSCHE NORM Normenausschuss Luft- und Raumfahrt (NL) im DINPreisgruppe 26DIN Deutsches Institut f r Normung e.V. Jede Art der Vervielf ltigung, auch auszugsweise, nur mit Genehmigung des DIN Deutsches Institut f r Normung e. V., Berlin, gestattet.ICS 49.140?=“ 9575528www.din.deXDIN EN
2、14777Raumfahrttechnik Multipaction Konzeption und Test;Englische Fassung EN 14777:2004Space engineering Multipaction design and test;English version EN 14777:2004Systmes sol et oprations Conception et test prenant en compte l effet Multipactor;Version anglaise EN 14777:2004Alleinverkauf der Normen d
3、urch Beuth Verlag GmbH, 10772 Berlin www.beuth.deGesamtumfang 72 SeitenDIN EN 14777:2005-10 2 Nationales Vorwort Die European Cooperation for Space Standardization (ECSS), eine Einrichtung zur Erstellung eines kohrenten, einheitlichen Normenwerkes zur Anwendung in allen europischen Raumfahrtprojekte
4、n, hat am 1996-11-13 vom Europischen Komitee fr Normung (CEN) das Mandat (M/237) erhalten, fr den CEN-Subsector T02 Aerospace Europische Normen (EN) auszuarbeiten. Aufgrund der zwischen ISO/TC 20/SC 14 Raumfahrt und ECSS vereinbarten A-Liaison werden die Normungsprogramme dieser Partner abgestimmt u
5、nd die Abstimmungsregeln gem Abschnitt 5.2 der Wiener Vereinbarung angewendet. Die vorliegende Norm EN 14777:2004 wurde von CEN/CS T02 auf Basis der ECSS-E-20-01 erarbeitet. EUROPEAN STANDARD NORME EUROPENNE EUROPISCHE NORM EN 14777 July 2004 ICS 49.140 English version Space engineering - Multipacti
6、on design and test Systmes sol et oprations - Conception et test prenant en compte leffet Multipactor Raumfahrttechnik Multipaction Konzeption und Test This European Standard was approved by CEN on 29 April 2004. CEN members are bound to comply with the CEN/CENELEC Internal Regulations which stipula
7、te the conditions for giving this European Standard the status of a national standard without any alteration. Up-to-date lists and bibliographical references concerning such national standards may be obtained on application to the Central Secretariat or to any CEN member. This European Standard exis
8、ts in three official versions (English, French, German). A version in any other language made by translation under the responsibility of a CEN member into its own language and notified to the Central Secretariat has the same status as the official versions. CEN members are the national standards bod
9、ies of Austria, Belgium, Cyprus, Czech Republic, Denmark, Estonia, Finland, France, Germany, Greece, Hungary, Iceland, Ireland, Italy, Latvia, Lithuania, Luxembourg, Malta, Netherlands, Norway, Poland, Portugal, Slovakia, Slovenia, Spain, Sweden, Switzerland and United Kingdom. EUROPEAN COMMITTEE FO
10、R STANDARDIZATION COMIT EUROPEN DE NORMALISATION EUROPISCHES KOMITEE FR NORMUNG Management Centre: rue de Stassart, 36 B-1050 Brussels 2004 CEN All rights of exploitation in any form and by any means reserved worldwide for CEN national Members. Ref. No. EN 14777:2004: EEN 14777:2004 (E) 2 Contents P
11、age Foreword. 5 Introduction 6 1 Scope . 7 2 Normative references . 7 3 Terms, definitions and abbreviated terms . 8 3.1 Terms and definitions. 8 3.2 Abbreviated terms 10 4 Verification 10 4.1 Verification process 10 4.2 Verification levels . 11 4.3 Verification plan 11 4.3.1 Introduction . 11 4.3.2
12、 Generation and updating . 11 4.3.3 Description 11 4.4 Verification routes 12 4.5 Classification of component type . 12 4.6 Single carrier . 13 4.6.1 General. 13 4.6.2 Margins 13 4.6.3 Route to demonstrate conformance . 14 4.7 Multi-carrier . 16 4.7.1 General. 16 4.7.2 Threshold above equivalent CW
13、peak power 16 4.7.3 Threshold below equivalent CW peak power. 16 4.7.4 Route to demonstrate conformance . 17 5 Design analyses 19 5.1 General. 19 5.2 Field analysis 19 5.3 Critical region identification 19 5.4 Multipaction sensitivity analysis. 20 5.5 Venting analysis 21 5.6 Inspection 21 6 Test con
14、ditions . 21 6.1 Cleanliness 21 6.2 Pressure. 21 6.3 Temperature 21 6.4 Frequencies. 22 6.5 Pulse duration . 22 6.5.1 General. 22 6.5.2 CW units. 22 6.5.3 Pulse units. 23 6.6 Electron seeding . 23 6.6.1 CW test. 23 6.6.2 Pulsed test. 23 6.6.3 Multi-carrier test 23 6.6.4 Seeding sources . 23 EN 14777
15、:2004 (E) 3 7 Methods of detection 24 7.1 General .24 7.2 Detection methods 24 7.3 Detection method parameters24 7.3.1 Sensitivity.24 7.3.2 Rise time.25 8 Test procedures.25 8.1 Test configurations .25 8.2 Test facility validation .25 8.3 Test execution26 8.3.1 General .26 8.3.2 Test procedure.26 8.
16、4 Acceptance criteria .27 8.4.1 General .27 8.4.2 Multi-carrier test.27 Annex A (informative) Multipaction background 28 A.1 Physics of multipaction 28 A.2 Other physical processes.29 A.3 RF operating environment29 A.4 Parallel plate multipaction35 A.5 Coaxial line multipaction 40 Annex B (informati
17、ve) Component venting 43 B.1 Introduction43 B.2 Discharge dependence on pressure43 B.3 Test example43 B.4 Venting dimensions 44 B.5 Venting hole calculations .44 B.6 Payload vacuum 44 B.7 Venting model used 44 B.8 Pumping conductance of a venting hole 45 B.9 Ultimate pressure 46 B.10 Venting experim
18、ent .48 B.11 Venting guidelines.48 Annex C (normative) Cleaning, handling, storage and contamination.50 C.1 Generic processes 50 C.2 Cleaning, handling and storage.50 C.3 Contaminants.52 Annex D (normative) Electron seeding 55 D.1 Introduction55 D.2 CW test .55 D.3 Pulsed test55 D.4 Multi-carrier te
19、st.55 D.5 Types of seeding source 57 Annex E (informative) Test methods58 E.1 Introduction58 E.2 General test methods58 E.3 Transient tests methods .62 E.4 Test facility validation .69 Bibliography70 Figures Figure 1 Routes to conformance for single carrier.15 Figure 2 Routes to conformance for mult
20、i-carrier case18 EN 14777:2004 (E) 4 Figure 3 The susceptibility zone boundaries for aluminium, copper, silver, gold and alodine 1200. 20 Figure A.1 Total secondary electron emission as a function of energy of the incident electron. 36 Figure A.2 Multipaction susceptibility zones for parallel plates
21、 of aluminum 37 Figure A.3 Multipaction thresholds for all materials studied, plotted in a single graph as labeled 42 Figure B.1 The basic venting model 45 Figure E.1 Generic close to carrier noise multipaction test site 59 Figure E.2 Principal multipaction test set-up for nulling detection method .
22、 61 Figure E.3 Test configuration (mode 1). 63 Figure E.4 Test configuration (mode 2). 64 Figure E.5 Detected envelope of a five carrier waveform . 66 Figure E.6 Charge probe. 68 Tables Table A.1 Worst case mode order for susceptible gaps for gold 31 Table A.2 Worst case mode order for susceptible g
23、aps for silver. 32 Table A.3 Worst case mode order for susceptible gaps for aluminium 33 Table A.4 Worst case mode order for susceptible gaps for alodine . 34 Table A.5 Worst case mode order for susceptible gaps for copper 35 Table A.6 Constants for the most used materials . 40 Table A.7 Critical vo
24、ltages for multipaction in 50 coaxial lines 41 Table B.1 Outgassing rate for space components used in space applications 46 EN 14777:2004 (E) 5 Foreword This document (EN 14777:2004) has been prepared by CEN. This European Standard shall be given the status of a national standard, either by publicat
25、ion of an identical text or by endorsement, at the latest by January 2005, and conflicting national standards shall be withdrawn at the latest by January 2005. It is based on a previous version1)originally prepared by the ECSS E-20-01 Working Group, reviewed by the ECSS Engineering Panel and approve
26、d by the ECSS Steering Board. The European Cooperation for Space Standardization (ECSS) is a cooperative effort of the European Space Agency, National Space Agencies and European industry associations for the purpose of developing and maintaining common standards. This European Standard is one of th
27、e series of space standards intended to be applied together for the management, engineering and product assurance in space projects and applications. Requirements in this European Standard are defined in terms of what shall be accomplished, rather than in terms of how to organize and perform the nec
28、essary work. This allows existing organizational structures and methods to be applied where they are effective, and for the structures and methods to evolve as necessary without rewriting the standards. The formulation of this European Standard takes into account the existing EN ISO 9000 family of d
29、ocuments. According to the CEN/CENELEC Internal Regulations, the national standards organizations of the following countries are bound to implement this European Standard: Austria, Belgium, Cyprus, Czech Republic, Denmark, Estonia, Finland, France, Germany, Greece, Hungary, Iceland, Ireland, Italy,
30、Latvia, Lithuania, Luxembourg, Malta, Netherlands, Norway, Poland, Portugal, Slovakia, Slovenia, Spain, Sweden, Switzerland and United Kingdom. 1)ECSS-E-20-01 EN 14777:2004 (E) 6 Introduction Single carrier multipaction has well-established theoretical and testing procedures, and the heritage from p
31、roven components enables to define testing margin values as requirements for European space missions. Applying the single carrier margin to peak in-phase multi-carrier signals is recognized as excessively onerous in many cases, but the present understanding of multipaction for multicarrier signals i
32、s not well enough established for a reduced limit to be specified. For this reason, the margins for the multi-carrier case are stated as recommendations, with a view to their evolving to requirements in the longer term. EN 14777:2004 (E) 7 1 Scope This document specifies the requirements and recomme
33、ndations for the design and test of RF components and equipment to achieve acceptable performance with respect to multipaction-free operation in service in space. The document includes: verification planning requirements; definition of a route to conform to the requirements; design and test margin r
34、equirements; design and test requirements; and informative annexes that provide guidelines on the design and test processes. This document is intended to result in the effective design and verification of the multipaction performance of the equipment and consequently in a high confidence in achievin
35、g successful product operation. This document covers multipaction events occurring in all classes of RF satellite components and equipment at all frequency bands of interest. Operation in single carrier CW and pulse modulated mode are included, as well as multi-carrier operations. This document does
36、 not include breakdown processes caused by collisional processes, such as plasma formation. This document is applicable to all space missions. When viewed in a specific project context, the requirements defined in this document should be tailored to match the genuine requirements of a particular pro
37、file and circumstances of a project. NOTE Tailoring is a process by which individual requirements of specifications, standards and related documents are evaluated and made applicable to a specific project, by selection and in some exceptional cases, modification of existing or addition of new requir
38、ements. 2 Normative references The following referenced documents are indispensable for the application of this document. For dated references, only the edition cited applies. For undated references, the latest edition of the referenced document (including any amendments) applies. EN 13701:2001, Spa
39、ce systems Glossary of terms. EN 14725, Space engineering Verification. EN ISO 146441, Cleanrooms and associated controlled environments Part 1: Classification of air cleanliness (ISO 14644-1:1999). ESCC Basic Specification No. 24900, Issue 1, October 2002, Minimum requirements for controlling envir
40、onmental contamination of components. ESCC Basic Specification No. 20600, Issue 1, February 2003, Preservation, packaging and despatch of ESCC electronic components. EN 14777:2004 (E) 8 3 Terms, definitions and abbreviated terms 3.1 Terms and definitions For the purposes of this document, the terms
41、and definitions given in EN 13701:2001 and the following apply. 3.1.1 acceptance margin margin to use for acceptance testing 3.1.2 acceptance stage verification stage with the objective of demonstrating that the product is free of workmanship defects and integration errors and ready for its intended
42、 use 3.1.3 analysis uncertainty numerical value of the uncertainty associated with an analysis NOTE In performing analysis, a conservative approach based on pessimistic assumptions is used when assessing threshold powers for the onset of multipaction. 3.1.4 assembly (process) process of mechanical m
43、ating of hardware to obtain a low level configuration after the manufacturing process (see also EN 13701) 3.1.5 batch acceptance test test performed on a sample from each batch of flight units to verify that the units conform to the acceptance requirements NOTE For requirements on the sample size, s
44、ee 8.3.1.a. 3.1.6 design margin theoretically computed margin between the specified power handling of the component and the result of an analysis after the analysis uncertainty has been subtracted NOTE As for the analysis uncertainty, the worst case is used. 3.1.7 development test testing performed
45、during the design and development phase which can supplement the theoretical design activities 3.1.8 gap voltage voltage in the critical gap NOTE The critical gap corresponds to the most critical location in the space RF component where the multipaction can occur. 3.1.9 in-process test testing perfo
46、rmed during the manufacture of flight standard equipment EN 14777:2004 (E) 9 NOTE It is carried out with the equipment in an unfinished state or on a part or sub-assembly that cannot be tested fully when later integrated into the equipment. The tests form part of verification. 3.1.10 integration pro
47、cess of physically and functionally combining lower level products to obtain a particular functional configuration NOTE The term product can include hardware, software or both. 3.1.11 measurement uncertainty uncertainty with which the specified power level is applied to the test item 3.1.12 model ph
48、ilosophy definition of the optimum number and characteristics of physical models to achieve a high confidence in the product verification with the shortest planning and a suitable weighing of costs and risks 3.1.13 qualification margin margin between the specified power level and the power level at
49、which a qualification test is performed, taking into account the measurement uncertainty 3.1.14 qualification stage verification stage with the objective to demonstrate that the design conforms to the applicable requirements including proper margins 3.1.15 qualification test testing performed on a single flight standard unit to establish that a suitable margin exists in the design and build standard NOTE Such suitable margin is the qualification margin. 3.1.16 review-of-design verification method us
